Computational Aeroacoustics (CAA) requires accurate and stable schemes for solving acoustic and flow field directly. Those schemes have a high-order of truncation and high-resolution characteristics in the evaluation of spatial derivatives, have the GRID stability and maintain numerical or physical conservation properties. Optimized high-order compact (OHOC) schemes, which have high resolution and low dissipation-dispersion error, have been developed and applied for Computational Aeroacoustics (CAA) problems. Previously, the optimized high-order compact (OHOC) schemes are applied as finite difference schemes. However, Most of finite difference schemes have difficulties in obtaining flow properties especially for non-smoothing GRID. In this thesis, the optimized high-order compact (OHOC) schemes are studied for finite volume schemes, which is insensitive to the GRID system in general. Special treatment of surface boundary condition is contrived in applying the Ghost Cell method, which is established according to normal flux derivatives at the boundary. For suppressing the numerical oscillations due to the discontinuities in the central schemes, an adaptive nonlinear artificial dissipation (ANAD) is used. OHOC scheme, for a finite volume scheme, is validated in 1-D linear wave problem, shock tube problem and 2-D Nozzle problem. A simple flow with acoustic perturbations is also solved with both the finite difference and the finite volume OHOC scheme. Two schemes are compared especially for a GRID system in which the interval of GRID changes suddenly. Finite volume OHOC scheme obtains more stable and accurate solutions than finite difference OHOC scheme.
